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25.1501 General. 25.1503 Airspeed limitations: general. 25.1541 General. 25.1581 General. |
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(a) Each operating limitation specified in Secs. 25.1503 through 25.1533 and other limitations and information necessary for safe operation must be established. (b) The operating limitations and other information necessary for safe operation must be made available to the crewmembers as prescribed in Secs. 25.1541 through 25.1587. [Amdt. 25-42, 43 FR 2323, Jan. 16, 1978] |
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When airspeed limitations are a function of weight, weight distribution, altitude, or Mach number, limitations corresponding to each critical combination of these factors must be established. Sec. 25.1505 Maximum operating limit speed. The maximum operating limit speed (VMO/MMO airspeed or Mach Number, whichever is critical at a particular altitude) is a speed that may not be deliberately exceeded in any regime of flight (climb, cruise, or descent), unless a higher speed is authorized for flight test or pilot training operations. VMO/MMO must be established so that it is not greater than the design cruising speed VC and so that it is sufficiently below VD/MD or VDF/ MDF, to make it highly improbable that the latter speeds will be inadvertently exceeded in operations. The speed margin between VMO/MMO and VD/MD or VDFM/DF may not be less than that determined under Sec. 25.335(b) or found necessary during the flight tests conducted under Sec. 25.253. [Amdt. 25-23, 35 FR 5680, Apr. 8, 1970] Sec. 25.1507 Maneuvering speed. The maneuvering speed must be established so that it does not exceed the design maneuvering speed VA determined under Sec. 25.335(c). Sec. 25.1511 Flap extended speed. The established flap extended speed VFE must be established so that it does not exceed the design flap speed VF chosen under Secs. 25.335(e) and 25.345, for the corresponding flap positions and engine powers. Sec. 25.1513 Minimum control speed. The minimum control speed VMC determined under Sec. 25.149 must be established as an operating limitation. Sec. 25.1515 Landing gear speeds. (a) The established landing gear operating speed or speeds, VLO, may not exceed the speed at which it is safe both to extend and to retract the landing gear, as determined under Sec. 25.729 or by flight characteristics. If the extension speed is not the same as the retraction speed, the two speeds must be designated as VLO(EXT) and VLO(RET), respectively. (b) The established landing gear extended speed VLE may not exceed the speed at which it is safe to fly with the landing gear secured in the fully extended position, and that determined under Sec. 25.729. [Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as amended by Amdt. 25-38, 41 FR 55468, Dec. 20, 1976] Sec. 25.1517 Rough air speed, VRA. A rough air speed, VRA, for use as the recommended turbulence penetration airspeed in Sec. 25.1585(a)(8), must be established, which-- (1) Is not greater than the design airspeed for maximum gust intensity, selected for VB; and (2) Is not less than the minimum value of VB specified in Sec. 25.335(d); and (3) Is sufficiently less than VMO to ensure that likely speed variation during rough air encounters will not cause the overspeed warning to operate too frequently. In the absence of a rational investigation substantiating the use of other values, VRA must be less than VMO--35 knots (TAS). [Amdt. 25-86, 61 FR 5222, Feb. 9, 1996] Sec. 25.1519 Weight, center of gravity, and weight distribution. The airplane weight, center of gravity, and weight distribution limitations determined under Secs. 25.23 through 25.27 must be established as operating limitations. Sec. 25.1521 Powerplant limitations. (a) General. The powerplant limitations prescribed in this section must be established so that they do not exceed the corresponding limits for which the engines or propellers are type certificated and do not exceed the values on which compliance with any other requirement of this part is based. (b) Reciprocating engine installations. Operating limitations relating to the following must be established for reciprocating engine installations: (1) Horsepower or torque, r.p.m., manifold pressure, and time at critical pressure altitude and sea level pressure altitude for-- (i) Maximum continuous power (relating to unsupercharged operation or to operation in each supercharger mode as applicable); and (ii) Takeoff power (relating to unsupercharged operation or to operation in each supercharger mode as applicable). (2) Fuel grade or specification. (3) Cylinder head and oil temperatures. (4) Any other parameter for which a limitation has been established as part of the engine type certificate except that a limitation need not be established for a parameter that cannot be exceeded during normal operation due to the design of the installation or to another established limitation. (c) Turbine engine installations. Operating limitations relating to the following must be established for turbine engine installations: (1) Horsepower, torque or thrust, r.p.m., gas temperature, and time for-- (i) Maximum continuous power or thrust (relating to augmented or unaugmented operation as applicable). (ii) Takeoff power or thrust (relating to augmented or unaugmented operation as applicable). (2) Fuel designation or specification. (3) Any other parameter for which a limitation has been established as part of the engine type certificate except that a limitation need not be established for a parameter that cannot be exceeded during normal operation due to the design of the installation or to another established limitation. (d) Ambient temperature. An ambient temperature limitation (including limitations for winterization installations, if applicable) must be established as the maximum ambient atmospheric temperature established in accordance with Sec. 25.1043(b). [Doc. No. 24344, Amdt. 25-72, 55 FR 29786, July 20, 1990] Sec. 25.1522 Auxiliary power unit limitations. If an auxiliary power unit is installed in the airplane, limitations established for the auxiliary power unit, including categories of operation, must be specified as operating limitations for the airplane. [Doc. No. 24344, Amdt. 25-72, 55 FR 29786, July 20, 1990] Sec. 25.1523 Minimum flight crew. The minimum flight crew must be established so that it is sufficient for safe operation, considering-- (a) The workload on individual crewmembers; (b) The accessibility and ease of operation of necessary controls by the appropriate crewmember; and (c) The kind of operation authorized under Sec. 25.1525. The criteria used in making the determinations required by this section are set forth in Appendix D. [Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as amended by Amdt. 25-3, 30 FR 6067, Apr. 29, 1965] Sec.25.1525 Kinds of operation. The kinds of operation to which the airplane is limited are established by the category in which it is eligible for certification and by the installed equipment. Sec.25.1527 Maximum operating altitude. The maximum altitude up to which operation is allowed, as limited by flight, structural, powerplant, functional, or equipment characteristics, must be established. Sec.25.1529 Instructions for Continued Airworthiness. The applicant must prepare Instructions for Continued Airworthiness in accordance with Appendix H to this part that are acceptable to the Administrator. The instructions may be incomplete at type certification if a program exists to ensure their completion prior to delivery of the first airplane or issuance of a standard certificate of airworthiness, whichever occurs later. [Amdt. 25-54, 45 FR 60173, Sept. 11, 1980] Sec.25.1531 Maneuvering flight load factors. Load factor limitations, not exceeding the positive limit load factors determined from the maneuvering diagram in Sec. 25.333(b), must be established. Sec.25.1533 Additional operating limitations. (a) Additional operating limitations must be established as follows: (1) The maximum takeoff weights must be established as the weights at which compliance is shown with the applicable provisions of this part (including the takeoff climb provisions of Sec. 25.121(a) through (c), for altitudes and ambient temperatures). (2) The maximum landing weights must be established as the weights at which compliance is shown with the applicable provisions of this part (including the landing and approach climb provisions of Secs. 25.119 and 25.121(d) for altitudes and ambient temperatures). (3) The minimum takeoff distances must be established as the distances at which compliance is shown with the applicable provisions of this part (including the provisions of Secs. 25.103 and 25.113, for weights, altitudes, temperatures, wind components, and runway gradients). (b) The extremes for variable factors (such as altitude, temperature, wind, and runway gradients) are those at which compliance with the applicable provisions of this part is shown. [Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as
amended by Amdt. 25-38, 41 FR 55468, Dec. 20, 1976; Amdt.
25-72, 55 FR 29786, July 20, 1990] |
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(a) The airplane must contain-- (1) The specified markings and placards; and (2) Any additional information, instrument markings, and placards required for the safe operation if there are unusual design, operating, or handling characteristics. (b) Each marking and placard prescribed in paragraph (a) of this section-- (1) Must be displayed in a conspicuous place; and (2) May not be easily erased, disfigured, or obscured. Sec. 25.1543 Instrument markings: general. For each instrument-- (a) When markings are on the cover glass of the instrument, there must be means to maintain the correct alignment of the glass cover with the face of the dial; and (b) Each instrument marking must be clearly visible to the appropriate crewmember. [Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as amended by Amdt. 25-72, 55 FR 29786, July 20, 1990] Sec. 25.1545 Airspeed limitation information. The airspeed limitations required by Sec. 25.1583 (a) must be easily read and understood by the flight crew. Sec. 25.1547 Magnetic direction indicator. (a) A placard meeting the requirements of this section must be installed on, or near, the magnetic direction indicator. (b) The placard must show the calibration of the instrument in level flight with the engines operating. (c) The placard must state whether the calibration was made with radio receivers on or off. (d) Each calibration reading must be in terms of magnetic heading in not more than 45 degree increments. Sec. 25.1549 Powerplant and auxiliary power unit instruments. For each required powerplant and auxiliary power unit instrument, as appropriate to the type of instrument-- (a) Each maximum and, if applicable, minimum safe operating limit must be marked with a red radial or a red line; (b) Each normal operating range must be marked with a green arc or green line, not extending beyond the maximum and minimum safe limits; (c) Each takeoff and precautionary range must be marked with a yellow arc or a yellow line; and (d) Each engine, auxiliary power unit, or propeller speed range that is restricted because of excessive vibration stresses must be marked with red arcs or red lines. [Amdt. 25-40, 42 FR 15044, Mar. 17, 1977] Sec. 25.1551 Oil quantity indication. Each oil quantity indicating means must be marked to indicate the quantity of oil readily and accurately. [Doc. No. 24344, Amdt. 25-72, 55 FR 29786, July 20, 1990] Sec. 25.1553 Fuel quantity indicator. If the unusable fuel supply for any tank exceeds one gallon, or five percent of the tank capacity, whichever is greater, a red arc must be marked on its indicator extending from the calibrated zero reading to the lowest reading obtainable in level flight. Sec. 25.1555 Control markings. (a) Each cockpit control, other than primary flight controls and controls whose function is obvious, must be plainly marked as to its function and method of operation. (b) Each aerodynamic control must be marked under the requirements of Secs. 25.677 and 25.699. (c) For powerplant fuel controls-- (1) Each fuel tank selector control must be marked to indicate the position corresponding to each tank and to each existing cross feed position; (2) If safe operation requires the use of any tanks in a specific sequence, that sequence must be marked on, or adjacent to, the selector for those tanks; and (3) Each valve control for each engine must be marked to indicate the position corresponding to each engine controlled. (d) For accessory, auxiliary, and emergency controls-- (1) Each emergency control (including each fuel jettisoning and fluid shutoff must be colored red; and (2) Each visual indicator required by Sec. 25.729(e) must be marked so that the pilot can determine at any time when the wheels are locked in either extreme position, if retractable landing gear is used. Sec. 25.1557 Miscellaneous markings and placards. (a) Baggage and cargo compartments and ballast location. Each baggage and cargo compartment, and each ballast location must have a placard stating any limitations on contents, including weight, that are necessary under the loading requirements. However, underseat compartments designed for the storage of carry-on articles weighing not more than 20 pounds need not have a loading limitation placard. (b) Powerplant fluid filler openings. The following apply: (1) Fuel filler openings must be marked at or near the filler cover with-- (i) The word "fuel"; (ii) For reciprocating engine powered airplanes, the minimum fuel grade; (iii) For turbine engine powered airplanes, the permissible fuel designations; and (iv) For pressure fueling systems, the maximum permissible fueling supply pressure and the maximum permissible defueling pressure. (2) Oil filler openings must be marked at or near the filler cover with the word "oil". (3) Augmentation fluid filler openings must be marked at or near the filler cover to identify the required fluid. (c) Emergency exit placards. Each emergency exit placard must meet the requirements of Sec. 25.811. (d) Doors. Each door that must be used in order to reach any required emergency exit must have a suitable placard stating that the door is to be latched in the open position during takeoff and landing. [Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as amended by Amdt. 25-32, 37 FR 3972, Feb. 24, 1972; Amdt. 25-38, 41 FR 55468, Dec. 20, 1976; Amdt. 25-72, 55 FR 29786, July 20, 1990] Sec. 25.1561 Safety equipment. (a) Each safety equipment control to be operated by the crew in emergency, such as controls for automatic liferaft releases, must be plainly marked as to its method of operation. (b) Each location, such as a locker or compartment, that carries any fire extinguishing, signaling, or other life saving equipment must be marked accordingly. (c) Stowage provisions for required emergency equipment must be conspicuously marked to identify the contents and facilitate the easy removal of the equipment. (d) Each liferaft must have obviously marked operating instructions. (e) Approved survival equipment must be marked for identification and method of operation. [Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as amended by Amdt. 25-46, 43 FR 50598, Oct. 30, 1978] Sec. 25.1563 Airspeed placard. A placard showing the maximum airspeeds for flap
extension for the takeoff, approach, and landing positions
must be installed in clear view of each pilot. |
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(a) Furnishing information. An Airplane Flight Manual must be furnished with each airplane, and it must contain the following: (1) Information required by Secs. 25.1583 through 25.1587. (2) Other information that is necessary for safe operation because of design, operating, or handling characteristics. (3) Any limitation, procedure, or other information established as a condition of compliance with the applicable noise standards of part 36 of this chapter. (b) Approved information. Each part of the manual listed in Secs. 25.1583 through 25.1587, that is appropriate to the airplane, must be furnished, verified, and approved, and must be segregated, identified, and clearly distinguished from each unapproved part of that manual. (c) [Reserved] (d) Each Airplane Flight Manual must include a table of contents if the complexity of the manual indicates a need for it. [Amdt. 25-42, 43 FR 2323, Jan. 16, 1978, as amended by Amdt. 25-72, 55 FR 29786, July 20, 1990] Sec. 25.1583 Operating limitations. (a) Airspeed limitations. The following airspeed limitations and any other airspeed limitations necessary for safe operation must be furnished: (1) The maximum operating limit speed VMO/MMO and a statement that this speed limit may not be deliberately exceeded in any regime of flight (climb, cruise, or descent) unless a higher speed is authorized for flight test or pilot training. (2) If an airspeed limitation is based upon compressibility effects, a statement to this effect and information as to any symptoms, the probable behavior of the airplane, and the recommended recovery procedures. (3) The maneuvering speed VA and a statement that full application of rudder and aileron controls, as well as maneuvers that involve angles of attack near the stall, should be confined to speeds below this value. (4) The flap extended speed VFE and the pertinent flap positions and engine powers. (5) The landing gear operating speed or speeds, and a statement explaining the speeds as defined in Sec. 25.1515(a). (6) The landing gear extended speed VLE, if greater than VLO, and a statement that this is the maximum speed at which the airplane can be safely flown with the landing gear extended. (b) Powerplant limitations. The following information must be furnished: (1) Limitations required by Sec. 25.1521 and Sec. 25.1522. (2) Explanation of the limitations, when appropriate. (3) Information necessary for marking the instruments required by Secs. 25.1549 through 25.1553. (c) Weight and loading distribution. The weight and center of gravity limits required by Secs. 25.25 and 25.27 must be furnished in the Airplane Flight Manual. All of the following information must be presented either in the Airplane Flight Manual or in a separate weight and balance control and loading document which is incorporated by reference in the Airplane Flight Manual: (1) The condition of the airplane and the items included in the empty weight as defined in accordance with Sec. 25.29. (2) Loading instructions necessary to ensure loading of the airplane within the weight and center of gravity limits, and to maintain the loading within these limits in flight. (3) If certification for more than one center of gravity range is requested, the appropriate limitations, with regard to weight and loading procedures, for each separate center of gravity range. (d) Flight crew. The number and functions of the minimum flight crew determined under Sec. 25.1523 must be furnished. (e) Kinds of operation. The kinds of operation approved under Sec. 25.1525 must be furnished. (f) Altitudes. The altitude established under Sec. 25.1527. (g) [Reserved] (h) Additional operating limitations. The operating limitations established under Sec.25.1533 must be furnished. (i) Maneuvering flight load factors. The positive maneuvering limit load factors for which the structure is proven, described in terms of accelerations, must be furnished. [Doc. No. 5066, 29 FR 1891, Dec. 24, 1964, as amended by Amdt. 25-38, 41 FR 55468, Dec, 20, 1976; Amdt. 25-42, 43 FR 2323, Jan. 16, 1978; Amdt. 25-46, 43 FR 50598, Oct. 30, 1978; Amdt. 25-72, 55 FR 29787, July 20, 1990] Sec. 25.1585 Operating procedures. (a) Information and instructions regarding the peculiarities of normal operations (including starting and warming the engines, taxiing, operation of wing flaps, landing gear, and the automatic pilot) must be furnished, together with recommended procedures for-- (1) Engine failure (including minimum speeds, trim, operation of the remaining engines, and operation of flaps); (2) Stopping the rotation of propellers in flight; (3) Restarting turbine engines in flight (including the effects of altitude); (4) Fire, decompression, and similar emergencies; (5) Ditching (including the procedures based on the requirements of Secs. 25.801, 25.807(d), 25.1411, and 25.1415 (a) through (e)); (6) Use of ice protection equipment; (7) Use of fuel jettisoning equipment, including any operating precautions relevant to the use of the system; (8) Operation in turbulence for turbine powered airplanes (including recommended turbulence penetration airspeeds, flight peculiarities, and special control instructions); (9) Restoring a deployed thrust reverser intended for ground operation only to the forward thrust position in fight or continuing fight and landing with the thrust reverser in any position except forward thrust; and (10) Disconnecting the battery from its charging source, if compliance is shown with Sec. 25.1353 (c)(6)(ii) or (c)(6)(iii). (b) Information identifying each operating condition in which the fuel system independence prescribed in Sec. 25.953 is necessary for safety must be furnished, together with instructions for placing the fuel system in a configuration used to show compliance with that section. (c) The buffet onset envelopes determined under Sec. 25.251 must be furnished. The buffet onset envelopes presented may reflect the center of gravity at which the airplane is normally loaded during cruise if corrections for the effect of different center of gravity locations are furnished. (d) Information must be furnished which indicates that when the fuel quantity indicator reads "zero" in level flight, any fuel remaining in the fuel tank cannot be used safely in flight. (e) Information on the total quantity of usable fuel for each fuel tank must be furnished. [Doc. No. 5066, 29 FR 18291, Dec. 24, 1964, as amended by Amdt. 25-11, 32 FR 6913, May 5, 1967; Amdt. 25-23, 35 FR 5680, Apr. 8, 1970; Amdt. 25-40, 42 FR 15044, Mar. 17, 1977; Amdt. 25-42, 43 FR 2323, Jan 16, 1978; Amdt. 25-46, 43 FR 50598, Oct. 30, 1978] Sec. 25.1587 Performance information. (a) Each Airplane Flight Manual must contain information to permit conversion of the indicated temperature to free air temperature if other than afree air temperature indicator is used to comply with the requirements of Sec. 25.1303(a)(1). (b) Each Airplane Flight Manual must contain the performance information computed under the applicable provisions of this part for the weights, altitudes, temperatures, wind components, and runway gradients, as applicable, within the operational limits of the airplane, and must contain the following: (1) The conditions under which the performance information was obtained, including the speeds associated with the performance information. (2) Vs determined in accordance with Sec. 25.103. (3) The following performance information (determined by extrapolation and computed for the range of weights between the maximum landing and maximum takeoff weights): (i) Climb in the landing configuration. (ii) Climb in the approach configuration. (iii) Landing distance. (4) Procedures established under Sec. 25.101 (f), (g), and (h) that are related to the limitations and information required by Sec. 25.1533 and by this paragraph. These procedures must be in the form of guidance material, including any relevant limitations or information. (5) An explanation of significant or unusual flight or ground handling characteristics of the airplane. [Amdt. 25-42, 43 FR 2324, Jan. 16, 1978, as amended
by Amdt. 25-72, 55 FR 29787, July 20, 1990] |
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For more information on how ASTECH Engineering may be able to help you, please contact Jeff Wilson at astech@cox.net or call 316-304-6157. © Copyright 1996 ASTECH Engineering. All rights reserved. No part of this document may be reproduced in any form without the expressed written consent of the author. |
